WIND-TUNNEL INVESTIGATION AT HIGH SUBSONIC SPEEDS OF JET, SPOILER, AND AILERON CONTROLS ON A 1/16-SCALE MODEL OF THE DOUGLAS D-558-II RESEARCH AIRPLANE

Abstract

An investigation was made in the Langley high-speed 7- by 10-foot tunnel through a Mach number range from 0.60 to 0.96 to determine the characteristics of a wing trailing-edge jet control on a 1/16-scale model of the Douglas D-558-II research airplane. The control was operated with ram air obtained from wing-tip inlets. The characteristics of ailerons and trailing-edge spoilers were also obtained for comparison with the jet control.

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Document Details

Document Type
Technical Report
Publication Date
Jul 27, 1956
Accession Number
AD0102027

Entities

People

  • Raymond D. Vogler

Organizations

  • Langley Research Center

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aeronautical Laboratories
  • Aircrafts
  • Airplanes
  • Drag
  • Dynamic Pressure
  • Government Procurement
  • Governments
  • High Angles
  • Mach Number
  • Plenum Chambers
  • Research Aircraft
  • Scale Models
  • Stagnation Pressure
  • Trailing Edges
  • United States Government
  • Wind Tunnels
  • Wing Tips

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.